Aeroplane



HEHUIYHU l IUO Patented Dec. 18, 1923.

UNITED STATES J' OI-IN TRUNKO,`0F ARDEN, WEST VIRGINIA.

AEROPLANE.

Application filed May 8, 1923. Serial No. 637,511.

To all whom 'it may concern:

Be it known that I, JOHN TRUNKo, a citizen of Hungary, residing ,at Arden, in the county of Barbour and State of West Virginia, have invented certain new and useful Improvements in Aeroplanes, of which the following is a specification.

This invention relates to certain new and useful improvements in aeroplanes and particularly to that type having an adjustable wing or plane mounting wherein the planes are pivotally supported to vary the transverse axes thereof relative to the longitudinal axis of the fuselage to control the ascent and descent of the areoplane.

A further object of the invention resides in the provision of an aeroplane having adjustable side wings or planes simultaneously operable for varying the angularity thereof by the provision of a train of gearing that is manually operable.

With the above .and other objects in view as the nature of the invention is better understood, the same consists of the novel form, combination and arrangement of parts hereinafter more fully described, shown in the accompanying drawings7 and claimed.

In the accompanying drawings, wherein like reference characters designate corresponding parts throughout the several views,

Fig. 1 is a side elevational view of an aeroplane constructed in accordance with the present invention, showing the adjusted positions for the side wings or planes by dotted lines,

Fig. 2 is a top plan view of t-he aeroplane showing the pivotally mounted rudder at the rear end of the fuselage,

Fig. 3 is a fragmentary side elevational view, partly broken away showing the pivotal mounting of the plane and the guide members associated with the front and rear inner edges thereof,

Fig. 4 is a cross sectional view taken on line IV-IV of Fig. 3 showing the train of gearing for adjusting the planes,

Fig. 5 is .a detail sectional view taken on line V--V of Fig. 4.

Fig. 6 is a fragmentary top plan view of the rear end'of the fuselage showing the rudder in its shifted position by dotted lines, and

Fig. 7 is a detail sectional view taken on line VII-VII of Fig. 6 showing the pivotal mounting for the rudder.

Referring more in detail to the accompanying drawings, the reference numeral 1 designates the fuselage of an aeroplane having a motor driven propeller 2 located at the front end thereof, the fuselage carrying ground wheels 3 adjacent the front ond and a skid 4 at the rear end thereof.

The rudder 5 is disposed above the empennage 6 the rudder carrying a depending stub shaft 7, shown in detail in Fig. 7 extending through the empennage 6 and journaled in the bearing 8 beneath the empennage. Arms 9 project laterally of the rudder 5 and have flexible operating cords 10 secured to the outer ends thereof that lead forwardly through openings 12 in the fuselage and terminate at a point adjacent the operators seat 13 for manipulation thereof in shifting the rudder 5 as illustrated by dotted lines in Fig. 6.

A plane 14 extends laterally of each side of the fuselage 1 adjacent the forward end thereof, and each plane 14 carries a bearing shaft 15 journaled through the adjacent side wall of the fuselage 1 as shown in Fig. 4. The front and rear corner edges of the inner end of each plane is guided in its movements with respect to the fuselage 1 through the medium of arcuate guide plates 16 that are secured as at 17 to the fuselage with arcuate slots 18 formed in the guides 16. A pin 19 carried by each inner co-rner edge of the plane 14 extends through the slots 18 in the guides, the curvature of the arcuate slots 18 being coincident to the bearing shaft 15 as illustrated in Fig. 3, this arrangement forming a substantial brace for the adjustable planes 14.

The operating mechanism for adjusting the planes 14 to assume different degrees of angularity with respect to the longitudinal axis of the fuselage 1 includes a shaft 20 extending transversely within the fuselage and journaled in bearings 21, a bevel gear 22 being secured to each end of the shaft 20 while a bevel gear 23 is secured to the shaft intermediate the ends thereof. An angle bracket 24 supported on the platform 25 that also supports the bearings 21, has an operating shaft 26 perpendicula-rly journaled therein that carries a bevel gear 27 upon the lower end thereof in mesh with the bevel gear 23 as shown in Fig. 4, the upper end of the shaft 26 Carrying a wheel 28 to facilitate the operation thereof. Bracket arms 29 secured to the side walls of the fuselage l adjacent the opposite end of the shaft 20, each have a shaft 3() journaled therein, the lower end of each shaft carrying' a beveled gear 3l in mesh with the adjacent gear 22, while the upper end of each shaft 30 carries a bevel gear 32 that meshes with the bevel gear 33 upon the inner adjacent end of the bearing shaft l5 for the plane 14.

From the above detailed description of the device it is believed that the construction and operation thereof will at once be apparent, it being noted that the angularity of the planes 14 relative to the longitudinal axis of the fuselage l is readily varied by operating the shaft. 26 through the medium of the wheel 28 to cause the train of meshing gears to shift the bearing shaft l5 for the purpose of controlling;` the rise and descent of the aeroplane. The operating cords l() for the rudder 5 terminating' adjacent the operators seat 13, complete control of the aeroplane is possible at all times.

Thile there is herein shown and described the preferred embodiment of the present invention, it is nevertheless to be understood that minor changes may be made therein without departing from the spirit and scope of the invention as claimed.

Having thus described my invention, I claim:

In an aeroplane of the type described, a fuselage, a rudder at the rear end thereof, side planes journaled at their ends in the fuselage, guide means fOr the front and rear inner corner edges of each plane, means for simultaneously shifting the planes on their bearings, said guide means including arcuate slotted members secured to the outer side of the fuselage with the are thereof concentric with the pivotal mounting' of the planes, guide pins carried by the inner corner edges of the planes extending' through the slots of the guides, said shifting means including a shaft journaled transverselyY within the fuselage, brackets secured inwardly of the fuselage adjacent the ends of the shaft, a verti cal shaft journaled in each bracket, gear connections between the opposite ends of said transverse shaft and the lower ends of the vertical shafts, gear connections between the upper ends of the vertical shafts and bearings for the planes and manually operable means for the transverse shaft. s

In testimony whereof I afiix my signature.

JOHN TRUNKO. 

